US3061427A - Alloy of titanium - Google Patents
Alloy of titanium Download PDFInfo
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- US3061427A US3061427A US25281A US2528160A US3061427A US 3061427 A US3061427 A US 3061427A US 25281 A US25281 A US 25281A US 2528160 A US2528160 A US 2528160A US 3061427 A US3061427 A US 3061427A
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- alloy
- titanium
- strength
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- 229910001069 Ti alloy Inorganic materials 0.000 title description 2
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims description 13
- 229910052719 titanium Inorganic materials 0.000 claims description 12
- 239000010936 titanium Substances 0.000 claims description 12
- 229910052782 aluminium Inorganic materials 0.000 claims description 8
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 8
- ATJFFYVFTNAWJD-UHFFFAOYSA-N Tin Chemical compound [Sn] ATJFFYVFTNAWJD-UHFFFAOYSA-N 0.000 claims description 7
- 239000012535 impurity Substances 0.000 claims description 7
- 229910052718 tin Inorganic materials 0.000 claims description 7
- QCWXUUIWCKQGHC-UHFFFAOYSA-N Zirconium Chemical compound [Zr] QCWXUUIWCKQGHC-UHFFFAOYSA-N 0.000 claims description 6
- 229910052720 vanadium Inorganic materials 0.000 claims description 6
- LEONUFNNVUYDNQ-UHFFFAOYSA-N vanadium atom Chemical compound [V] LEONUFNNVUYDNQ-UHFFFAOYSA-N 0.000 claims description 6
- 229910052726 zirconium Inorganic materials 0.000 claims description 6
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 claims description 5
- 229910052750 molybdenum Inorganic materials 0.000 claims description 5
- 239000011733 molybdenum Substances 0.000 claims description 5
- 229910045601 alloy Inorganic materials 0.000 description 41
- 239000000956 alloy Substances 0.000 description 41
- 230000032683 aging Effects 0.000 description 9
- 238000005275 alloying Methods 0.000 description 4
- 238000001816 cooling Methods 0.000 description 3
- 238000010438 heat treatment Methods 0.000 description 3
- 239000003381 stabilizer Substances 0.000 description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 3
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 2
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 2
- 238000002844 melting Methods 0.000 description 2
- 230000008018 melting Effects 0.000 description 2
- 229910052751 metal Inorganic materials 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 150000002739 metals Chemical class 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 229910052760 oxygen Inorganic materials 0.000 description 2
- 239000001301 oxygen Substances 0.000 description 2
- 238000010791 quenching Methods 0.000 description 2
- 230000000171 quenching effect Effects 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 239000003795 chemical substances by application Substances 0.000 description 1
- 239000012612 commercial material Substances 0.000 description 1
- 230000000536 complexating effect Effects 0.000 description 1
- 238000005242 forging Methods 0.000 description 1
- 239000004615 ingredient Substances 0.000 description 1
- 239000013067 intermediate product Substances 0.000 description 1
- 238000011031 large-scale manufacturing process Methods 0.000 description 1
- 229910052757 nitrogen Inorganic materials 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 230000000087 stabilizing effect Effects 0.000 description 1
Images
Classifications
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C14/00—Alloys based on titanium
Definitions
- This invention relates to titanium base alloys and more particularly to a titanium base alloy which is heat treatable to high tensile strength.
- alpha type titanium base alloys are well known. These include high temperature strength, creep resistance, and weldability.
- the alpha type alloys are not appreciably heat treatable. Addition of a substantial proportion of beta stabilizing alloying elements can produce an alpha-beta type alloy which is heat treatable, but the advantages of the alpha type alloy will generally be to a large degree lost in compositions of this type heretofore used or proposed.
- Another object of this invention is to provide an improved titanium base alloy. Another object of this invention is to provide a highly heat treatable titanium base alloy. A further object of this invention is to provide a heat treatable titanium base alloy but which also possesses in useful measure attributes of an alpha type titanium alloy. Another object of this invention is to provide a heat treatable, titanium base alloy having a substantially flat aging response curve.
- This invention contemplates an alloy consisting essentially of about 5% aluminum, about 5% zirconium, about 5% tin, about 1% vanadium, and about 1% molybdenum with the balance substantially all titanium and incidental impurities.
- the alloy is characterized by good room temperature properties as well as elevated temperature properties, and is particularly characterized by being heat treatable to a strength level of over 200,000 pounds per square inch While retaining good ductility.
- the proportions of the alloying elements employed in the alloy of this invention are critical.
- the amounts of the alpha stabilizers, aluminum, zirconium, and tin, provide mechanical properties not found in other combinations of these metals. Hence there is some complexing action which produces the beneficial elfects when these three elements are present in about these amounts. While the percentages should be as close to 5% as possible, this precision can-not always be obtained in large scale production, but the percentage of aluminum should lie within the range of 4.5% to 5.5% while some slight additional leeway may be permitted in the amounts of tin and zirconium, these each should be within the range of 4% to 6%.
- vanadium and molybdenum are also critical and these should each be present in amount about 1%, and should be within the range of 0.7% to 1.3%. More than this will result in loss of ductility and a tendency towards embrittlement, and less will not provide suflicient heat treatment response.
- Incidental impurities such as oxygen, nitrogen, carbon, and various metals in impurity amounts, may be present in the alloy of this invention to the extent that they do not materially aifect the characteristic properties thereof. Such impurities should total less than about 0.5%, and the oxygen content alone should ordinarily be less than about 0.2%.
- the alloy is capable of being solution heat treated and aged to strengths of over 200,000 pounds per square inch.
- the curve identified as 1 shows that after solution heat treating at 1700? F. and water quenching, the alloy has an ultimate tensile strength of 163,000 pounds per square inch, and after a subsequent aging at 1000 F. for four hours, 1000 F. for eight hours or 1100 F. for two hours the ultimate tensile strengths were found to be 204,000; 205,000; and 205,000 pounds per square inch respectively. After an aging treatment of 1100 F. forfour hours the strength is only slightly lower at 199,000 pounds per square inch.
- the curve 2 shows that the yield strength under the same conditions of aging rose from 128,000 pounds per square inch to 185,000; 189,000; 194,000; and 188,000 pounds per square inch respectively.
- the percent elongation curve 3 shows value of 15% for the solution treated and water quenched alloy and 6%, 5.5% and 5% for the aged conditions at 1000 F. for 4 hours, 1000 F. for 8 hours and 1100 F. for 4 hours.
- Curves 4, 5, and 6 show, respectively, the ultimate tensile strength, yield strength and elongation of the alloy after solution heat treatment followed by air cooling, and subsequent aging. It is a unique feature that the alloy of this invention under these conditions shows substantially fiat aging curves. In curve 4 the ultimate tensile strength, after solution heat treating and air cooling, is 178,000 pounds per square inch and this value remains the same after aging at 1000 F. for 4 hours, or at 1l00 F. for 4 hours. The yield strength curve 5 rises only a.
- the alloy of this invention possesses a valuable combination of heat treat capabilities.
- it may be solution treated, quenched and aged to strengths of over 200,000 pounds per square inch for application where extremely high strength is required.
- it is also useful after solution treating and air cooling, at somewhat lower strength levels, in applications requiring uniformity of properties at normal and elevated temperatures, as in hot forming.
- the properties of the alloy of this invention are obtained with a total beta stabilizer content of only about 2%.
- the alloy possesses remarkably high heat treatment capability, yet retaining in good measure characteristics of an all alpha alloy.
- the following tables show the room temperature properties, elevated temperature properties and weldability (as determined by bend test on a weld) which will be shown by the 5Al-5Zr-5SnlMo-lV alloy compared to an alloy containing 6% aluminum and 4% vanadium and one containing 5% aluminum and 2.5% tin. Both these comparison alloys have enjoyed commercial success, the 6Al-4V alloy be- 3 oer ea?
- Table 3 compares elevated temperature strength and creep resistance of these alloys, and it will readily be seen that the Al-5Zr-5Sn-1Mo-1V alloy is superior to the 6Al-4V alloy and also superior to the 5Al-2.5Sn alpha alloy.
- T.S. and Y.S. Low values for T.S. and Y.S. are for mill annealed eonditinn,higl1 for high strength heat treated.
- the alloys of this invention may be produced by any convenient method.
- they may be produced by are melting, employing a consumable electrode of titanium sponge and the alloying elements in proper proportions.
- Such an electrode is progressively melted into a cooled crucible or mold to form a solid ingot.
- Such an ingot may be subjected to usual working procedures such as forging and rolling to provide intermediate products such as billet, bar, sheet, strip, and wire which may be further fabricated into shapes, forms, and elements useful in applications where titaniums light weight and strength are advantageous such as aircraft parts.
- An alloy consisting essentially of from 4.5% to 5.5% aluminum, from 4% to 6% zirconium, from 4% to 6% tin, from 0.7% to 1.3% molybdenum, and from 0.7% to 1.3% vanadium with the balance substantially all titanium and incidental impurities, characterized by being weldable and by being heat treatable to a tensile strength of over 200,000 pounds per square inch.
- An alloy consisting essentially of about 5% aluminum, about 5% zirconium, about 5% tin, about 1% molybdenum and about 1% vanadium with the balance substantially all titanium and incidental impurities, characterized by being weldable and by being heat treatable to a tensile strength of over 200,000 pounds per squalie inch.
Description
UTS,Ksi
0.2% YS, Ksi
ELONG., /o
Filed April 28, 1960 SOLUTION HEAT TREATED AT woo F,WATER QUENCHE -SOLUTION HEAT TREATED AT I700 F,AIR COOLED Zhrs. II00 F 4 hrs. 8 hrs. I000 F I000 F AGING TREATMENT None 4hrs. IIOO F INVENTOR. James V Lu hon Agent rates This invention relates to titanium base alloys and more particularly to a titanium base alloy which is heat treatable to high tensile strength.
The advantages of alpha type titanium base alloys are well known. These include high temperature strength, creep resistance, and weldability. The alpha type alloys, however, being composed of a one phase system, are not appreciably heat treatable. Addition of a substantial proportion of beta stabilizing alloying elements can produce an alpha-beta type alloy which is heat treatable, but the advantages of the alpha type alloy will generally be to a large degree lost in compositions of this type heretofore used or proposed.
It is therefore the principal object of this invention to provide an improved titanium base alloy. Another object of this invention is to provide a highly heat treatable titanium base alloy. A further object of this invention is to provide a heat treatable titanium base alloy but which also possesses in useful measure attributes of an alpha type titanium alloy. Another object of this invention is to provide a heat treatable, titanium base alloy having a substantially flat aging response curve. These and other objects of this invention will be apparent from the following description thereof.
This invention contemplates an alloy consisting essentially of about 5% aluminum, about 5% zirconium, about 5% tin, about 1% vanadium, and about 1% molybdenum with the balance substantially all titanium and incidental impurities. The alloy is characterized by good room temperature properties as well as elevated temperature properties, and is particularly characterized by being heat treatable to a strength level of over 200,000 pounds per square inch While retaining good ductility.
The proportions of the alloying elements employed in the alloy of this invention are critical. The amounts of the alpha stabilizers, aluminum, zirconium, and tin, provide mechanical properties not found in other combinations of these metals. Apparently there is some complexing action which produces the beneficial elfects when these three elements are present in about these amounts. While the percentages should be as close to 5% as possible, this precision can-not always be obtained in large scale production, but the percentage of aluminum should lie within the range of 4.5% to 5.5% while some slight additional leeway may be permitted in the amounts of tin and zirconium, these each should be within the range of 4% to 6%.
The amounts of vanadium and molybdenum are also critical and these should each be present in amount about 1%, and should be within the range of 0.7% to 1.3%. More than this will result in loss of ductility and a tendency towards embrittlement, and less will not provide suflicient heat treatment response.
Incidental impurities such as oxygen, nitrogen, carbon, and various metals in impurity amounts, may be present in the alloy of this invention to the extent that they do not materially aifect the characteristic properties thereof. Such impurities should total less than about 0.5%, and the oxygen content alone should ordinarily be less than about 0.2%.
The characteristics and unique properties of the alloy of this invention will be apparent from consideration of the data shown in the single FIGURE of the drawing.
3,061,427 Patented Oct. 30, 1962 The alloy for this work was produced by are melting the titanium and alloying ingredients. The melted ingot was then forged to sheet bar and rolled to 0.050 inch sheet. Specimen samples were machined from the sheet.
As seen in the figure the alloy is capable of being solution heat treated and aged to strengths of over 200,000 pounds per square inch. The curve identified as 1 shows that after solution heat treating at 1700? F. and water quenching, the alloy has an ultimate tensile strength of 163,000 pounds per square inch, and after a subsequent aging at 1000 F. for four hours, 1000 F. for eight hours or 1100 F. for two hours the ultimate tensile strengths were found to be 204,000; 205,000; and 205,000 pounds per square inch respectively. After an aging treatment of 1100 F. forfour hours the strength is only slightly lower at 199,000 pounds per square inch. The curve 2 shows that the yield strength under the same conditions of aging rose from 128,000 pounds per square inch to 185,000; 189,000; 194,000; and 188,000 pounds per square inch respectively.
The percent elongation curve 3 shows value of 15% for the solution treated and water quenched alloy and 6%, 5.5% and 5% for the aged conditions at 1000 F. for 4 hours, 1000 F. for 8 hours and 1100 F. for 4 hours.
few thousand pounds per square inch on aging, while the elongation curve 6 is essentially flat with the values in the solution heat treated and in the aged condition all and does not result in distortion which often accompanies.
a quenching operation.
Thus, the alloy of this invention possesses a valuable combination of heat treat capabilities. On the one hand, it may be solution treated, quenched and aged to strengths of over 200,000 pounds per square inch for application where extremely high strength is required. On the other hand, it is also useful after solution treating and air cooling, at somewhat lower strength levels, in applications requiring uniformity of properties at normal and elevated temperatures, as in hot forming.
It is of the utmost significance that the properties of the alloy of this invention are obtained with a total beta stabilizer content of only about 2%. At this beta stabilizer level the alloy possesses remarkably high heat treatment capability, yet retaining in good measure characteristics of an all alpha alloy. The following tables show the room temperature properties, elevated temperature properties and weldability (as determined by bend test on a weld) which will be shown by the 5Al-5Zr-5SnlMo-lV alloy compared to an alloy containing 6% aluminum and 4% vanadium and one containing 5% aluminum and 2.5% tin. Both these comparison alloys have enjoyed commercial success, the 6Al-4V alloy be- 3 oer ea? Room Temperature Tensile, Bend and Weld Bend Properties-Annealed U.'l.S., Y.S. Elong., Weld Alloy p.s.i. (0.2%), percent Bend T Ti-5.- .l-5Zr-5Sn-1lvI0-1V 156,000 147,000 13 9%(4/15 ase Ti-tiAl-4V 130,000 120,000 10 7 $4.5
yase Ti-5Al-2.5Sn b 115,000 110,000 10 2.5-5.0 (4
base).
' Ti-5Al-5Zr-5Sn-lMo-1V annealed 1,450" F.1 hour air 0001. b Ti-GAMV, Ti-5Al-2.5Sn commercial material as mill annealed.
Room Temperature Tensile, Bend and Weld Bend PropertiesHeat Treated U.'I.S., Y.S. Elong, Weld Bend Alloy p.s.i. (0.2%), percent T Ti-5Al-5Zr-5Sn-1Mo-1V 170,000 163,000 8 14.8-16.3
base).
Ti-GAl-V 183,000 175,000 4 N successtul bends base).
Table 3 below compares elevated temperature strength and creep resistance of these alloys, and it will readily be seen that the Al-5Zr-5Sn-1Mo-1V alloy is superior to the 6Al-4V alloy and also superior to the 5Al-2.5Sn alpha alloy.
1. TABLE 3 Elevated Temperature Tensile and Creep Properties Tensile Properties gtress for ree to Alloy 1.0% at Temp, U.I.S.,p.s.i. Y.S.(0.2%), 850 F. for F. p.s.i. 150 Hrs p.s.i.
Tl -5A1 -5Zr -5Sn -1Mo 750 152, 000 127, 000
1v 30,0110 89,000 i 731000 5 5,000 85-90000 1,000 8095,000 0045.000 i Ti-5Al-2.5Sn 750 77,00 05,000 40 000 li-5Al-5Zr-5Sn-1Mo-1V round bar heat treated 1,725 F.l hr. AC4-1,000 F.-2 hrs. AC. Room temperature strength approximately equivalent to 1,700 F.1/3 hr. AC+l,000 F.4 hrs. AC for sheet.
Low values for T.S. and Y.S. are for mill annealed eonditinn,higl1 for high strength heat treated.
It will be apparent from the above that neither thef 6Al-4V nor the 5A1-2.5Sn alloys possess the high tem-; perature strength or creep resistance of the alloy of this invention. The superiority of the 5Al-5Zr-5Sn-1Mo-1V composition in these respects must also be considered in view of its heat treatability which is also greater than either of these other alloys, and its Weldability.
The alloys of this invention may be produced by any convenient method. Advantageously they may be produced by are melting, employing a consumable electrode of titanium sponge and the alloying elements in proper proportions. Such an electrode is progressively melted into a cooled crucible or mold to form a solid ingot. Such an ingot may be subjected to usual working procedures such as forging and rolling to provide intermediate products such as billet, bar, sheet, strip, and wire which may be further fabricated into shapes, forms, and elements useful in applications where titaniums light weight and strength are advantageous such as aircraft parts.
I claim:
1. An alloy consisting essentially of from 4.5% to 5.5% aluminum, from 4% to 6% zirconium, from 4% to 6% tin, from 0.7% to 1.3% molybdenum, and from 0.7% to 1.3% vanadium with the balance substantially all titanium and incidental impurities, characterized by being weldable and by being heat treatable to a tensile strength of over 200,000 pounds per square inch.
2. An alloy consisting essentially of about 5% aluminum, about 5% zirconium, about 5% tin, about 1% molybdenum and about 1% vanadium with the balance substantially all titanium and incidental impurities, characterized by being weldable and by being heat treatable to a tensile strength of over 200,000 pounds per squalie inch.
References Cited in the file of this patent i UNITED STATES PATENTS 2,893,864 Harris et al. July 7, 1959
Claims (1)
1. AN ALLOY CONSISTING ESSENTIALLY OF FROM 4.5% TO 5.5% ALUMINUM, FROM 4% TO 6% ZIRCONIUM, FROM 4% TO 6% TIN, FROM 0.7% TO 1.3% MOLYBDENUM,AND FROM 0.7% TO 1.3% VANADIUM WITH THE BALANCE SUBSTANTIALLY ALL TITANIUM AND INCIDENTAL IMPURITIES, CHARACTERIZED BY BE-ING WELDABLE AND BY BEING HEAT TREATABLE TO A TENSILE STRENGTH OF OVER 200,000 POUNDS PER SQUARE INCH.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US25281A US3061427A (en) | 1960-04-28 | 1960-04-28 | Alloy of titanium |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US25281A US3061427A (en) | 1960-04-28 | 1960-04-28 | Alloy of titanium |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US3061427A true US3061427A (en) | 1962-10-30 |
Family
ID=21825106
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US25281A Expired - Lifetime US3061427A (en) | 1960-04-28 | 1960-04-28 | Alloy of titanium |
Country Status (1)
| Country | Link |
|---|---|
| US (1) | US3061427A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3343951A (en) * | 1963-10-17 | 1967-09-26 | Titanium Metals Corp | Titanium base alloy |
| US3364017A (en) * | 1966-05-10 | 1968-01-16 | Titanium Metals Corp | Titanium base alloys |
| US3451792A (en) * | 1966-10-14 | 1969-06-24 | Gen Electric | Brazed titanium structure |
| DE1558457B1 (en) * | 1966-05-12 | 1971-07-01 | Contimet Gmbh | USE OF A TITANIUM ALLOY FOR THE MANUFACTURING OF HIGHLY STRESSED STRUCTURAL PARTS FOR JET ENGINES |
| US3619184A (en) * | 1968-03-14 | 1971-11-09 | Reactive Metals Inc | Balanced titanium alloy |
| US4606886A (en) * | 1983-12-10 | 1986-08-19 | Imi Titanium Limited | Titanium-base alloy |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2893864A (en) * | 1958-02-04 | 1959-07-07 | Harris Geoffrey Thomas | Titanium base alloys |
-
1960
- 1960-04-28 US US25281A patent/US3061427A/en not_active Expired - Lifetime
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2893864A (en) * | 1958-02-04 | 1959-07-07 | Harris Geoffrey Thomas | Titanium base alloys |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3343951A (en) * | 1963-10-17 | 1967-09-26 | Titanium Metals Corp | Titanium base alloy |
| DE1533199B1 (en) * | 1963-10-17 | 1972-06-08 | Contimet Gmbh | USE OF A TITANIUM ALLOY FOR HEAT-RESISTANT AND CREEP-RESISTANT OBJECTS |
| US3364017A (en) * | 1966-05-10 | 1968-01-16 | Titanium Metals Corp | Titanium base alloys |
| DE1558457B1 (en) * | 1966-05-12 | 1971-07-01 | Contimet Gmbh | USE OF A TITANIUM ALLOY FOR THE MANUFACTURING OF HIGHLY STRESSED STRUCTURAL PARTS FOR JET ENGINES |
| US3451792A (en) * | 1966-10-14 | 1969-06-24 | Gen Electric | Brazed titanium structure |
| US3619184A (en) * | 1968-03-14 | 1971-11-09 | Reactive Metals Inc | Balanced titanium alloy |
| US4606886A (en) * | 1983-12-10 | 1986-08-19 | Imi Titanium Limited | Titanium-base alloy |
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